EngLib USM > Ω School of Aerospace Engineering >

Spirit global design challenge 2010 5 study on drag coefficient behavior of naca 0012 horizontal tail with multiple position¬/ Khor Fwu Woei

Spirit global design challenge 2010 5 study on drag coefficient behavior of naca 0012 horizontal tail with multiple position_Khor Fwu Woei_A2_2011_NI

Abstract Disertasi ini ialah satu kajian tentang pekali seretan bahagian ekor sebuah pesawat yang dihasilkan oleh pelbagai posisi/ tatarajah ekor mengufuk, di mana aerofoil NACA 0012 digunakan dalam kajian ini. Tujuan kajian ini adalah untuk menentukan tatarajah bahagian ekor pesawat yang dapat menghasilkan seretan paling minimum semasa rejim penerbangan yang berlainan seperti persiaran, perlepasan dan pendaratan. Untuk mencapai matlamat ini, analisis kaedah- kaedah berangka dalam dua dimensi dan tiga dimensi sedang diusahakan dengan bantuan perisian komputer dan beberapa pengiraan mudah menggunakan beberapa formula yang diperolehi dari buku rujukan.Dengan menggunakan perisian komersial Computational Fluid Dynamics (CFD seperti GAMBIT dan FLUENT, kajian atas aerofoil NACA 0012 dan seluruh bahagian ekor pesawat dapat dihasilkan. Penyelesai Navier Stoke berpangkalkan tekanan (PBNS) dan penyelesai Navier Stoke berpangkal kepadatan (DBNS), yang boleh didapati dalam perisisan FLUENT, adalah digunakan bersama-sama model kegeloraan seperti Inviscid, Spalart- Allmaras (S-A), Laminar, dan Reynolds Averaged Navier Stoke (RANS) κ-ω ke model masalah dinamik cecair dalam kelajuan subsonik dan transonik untuk memperoleh keputusan-keputusan yang boleh diharapkan dan dibandingkan dengan tesis atau data-data eksperimental. Kaedah sedemikian akan mewujudkan satu penyelesaian yang bersah untuk masalah dan dapat dijadikan sebagai rujukan untuk penyelidikan masa depan. ______________________________________________________________________________________ This dissertation is a study on the drag coefficient of an aircraft empennage produced by different position/configuration of horizontal tail, which in this case uses NACA 0012 airfoil. The purpose of the study is to determine which configuration of empennage produces the least drag during different flight regime such as in cruising, take-off and landing. In order to achieve this objective, numerical methods analysis on two dimensional and three dimensional models is being performed with the aid of computer software and some simple calculations using several formulas found. By using commercial Computational Fluid Dynamics (CFD) software like GAMBIT and FLUENT, the study on the NACA 0012 airfoil and the whole empennage can be simulated. Pressure based Navier Stoke (PBNS) solver and Density based Navier Stoke (DBNS) solver, which are available in FLUENT, are being applied together with Inviscid, Spalart- Allmaras (S-A), Laminar, and Reynolds Averaged Navier Stoke (RANS) κ-ω turbulence models to model the fluid dynamic problem in subsonic and transonic speed to obtain reliable results and compare with published or experimental data. Such method will establish a verified solution for the problem and may serve as a reference for future research.

Contributor(s): Khor Fwu Woei - Author Primary Item Type: Final Year Project Language: English Subject Keywords: aircraft empennage ; turbulence models; NACA 0012 airfoil First presented to the public: 5/1/2011 Original Publication Date: 7/31/2019 Previously Published By: Universiti Sains Malaysia Place Of Publication: School of Aerospace Engineering Citation: Extents: Number of Pages - 110 License Grantor / Date Granted:   / ( View License ) Date Deposited 2019-07-31 16:20:49.155 Submitter: Nor Hayati Ismail

All Versions

• Help | 
• About | 
• Privacy Policy